Warrior Study Guide

Piper Warrior III Study Guide

Page: 1 Revision: Original

Date: 07/01/2012

Introduction

This guide serves as a supplement to the PA-28-161 Piper Warrior III Pilot Operating Handbook(POH). This guide is not meant to act

as a replacement to the POH. In the event of a conflict of data between the study guide and the POH, the POH is the final

authority.

The purpose of this guide is to provide the student with a concise, simplified version of the main concepts of the POH. Using the

study guide is not intended to be a student’s sole source of aircraft knowledge but an additional source of information to be used to

help learn all of the applicable aircraft systems.

A Campus of the State University of New YorkFarmingdale State College● 2350 Broadhollow Road Farmingdale, New York 11735-1021

www.farmingdale.edu© Farmingdale State College 2012

http://www.farmingdale.edu/



Date: 07/01/2012

GENERAL DESCRIPTIONPA-28-161 WARRIOR III

I. IntroductionLow wing, Single Engine, Fixed Gear, All Metal Construction

II. General DescriptionA. Airframe

1. Aluminum Alloy Construction2. Steel Engine Mounts and Landing Gear3. Lightweight Plastics for wingtips, engine cowling,

and other nonstructural components.

B. Semi-Monocoque

C. Passenger Door On Right Side

D. Wing1. Conventional, Semi-Tapered2. Each Wing Contains One Fuel Tank

III. LimitationsA. Pilot Operating Handbook, Section Two

B. Airspeed Limitations1. VNE-160 KIAS2. VNO-126 KIAS3. VFE-103 KIAS4. VA 2400 lbs-111 KIAS

VA 1531 lbs-88 KIAS5. VY-79 KIAS6. VX-63 KIAS7. VS-50 KIAS8. VSO-44 KIAS9. VR-50 or 55(Dependant on Weight and

Configuration).






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C. Powerplant Limitations1. Lycoming O-320-D3G2. Maximum Horsepower-1603. Maximum RPM-27004. Maximum Oil Temp-245 F5. Minimum Oil Pressure-25 PSI6. Maximum Oil Pressure-115 PSI7. Minimum Fuel Pressure-0.5 PSI8. Maximum Fuel Pressure-8 PSI9. Fuel Grade-100 or 100LL Aviation Grade10. One Sensenich Propeller11. Minimum Propeller Diameter- 72 IN12. Maximum Propeller Diameter- 74 IN

D. Weight Limitations1. Maximum Ramp Wt- 2447lbs.2. Maximum Takeoff Wt- 2440lbs.3. Maximum Baggage Wt- 200lbs.

E. Flight Load Factors1. Positive Load Limit- 3.8G Normal, 4.4G Utility2. Negative Load Limit- No inverted maneuvers

allowed.

F. Fuel Limitations1. Total Capacity- 50 US Gallons2. Unusable Fuel- 2 US Gallons3. Usable Fuel- 48 US Gallons (24/Wing)

G. Placards

1. As per Section 2 of the PA-28-161 POH.

H. Crosswind

1. Maximum Demonstrated X-Wind- 17 KTS.






Date: 07/01/2012

POWERPLANT AND PROPELLERPA-28-161 WARRIOR III

I. Engine and PropellerA. Lycoming O-320-D3GB. 160HP at 2700RPMC. Four CylinderD. Horizontally Opposed (H)E. Air Cooled (A)F. Normally Aspirated (N)G. Direct Drive (D)H. Equipped With:

1. Starter2. 60 Amp, 28 Volt Alternator3. Two Magnetos4. Vacuum Pump5. Fuel Pump

II. Engine Controls

A. Throttle- Controls RPMB. Mixture- Controls Fuel to Air RatioC. Carburetor Heat- Controls Heated Air to Carburetor Inlet.

1. On- Unfiltered, Heated Air Through Hose Connected to Heater Shroud.

2. Off- Filtered Air From Chin Scoop on Lower Right Cowling.






Date: 07/01/2012

LANDING GEAR AND BRAKESPA-28-161 WARRIOR III

I. Landing Gear

A. Fixed GearB. Main Tire PSI at Max Gross Weight: 24 PSIC. Nose Tire PSI at Max Gross Weight: 30 PSID. Nose Tire: 5.00 x 5 Four-PlyE. Main Tire: 6.00 x 6 Four-PlyF. Nosewheel Steering

1. 20 or 30 degrees each side of center(30 if Nose Steering Bungee Installed).

2. Shimmy DampenerG. Air/Oil Oleo Struts

II. Brakes

A. Cleveland Single Disc Braked on Main Gear.B. Actuated by toe pedals.C. Hydraulic Cylinders located above each pedal.D. Brake Fluid

1. Top left front face of firewall.2. Red/Purple Color

E. Parking Brake1. Actuated by pulling back on brake lever and

depressing knob.






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FLIGHT CONTROLSPA-28-161 WARRIOR III

I. DescriptionA. Dual Connected Flight Yokes and Rudder PedalsB. Cables and Pulleys

II. Horizontal StabilatorA. Entire surface moves.B. Trailing edge anti-servo tab.

1. Moves in same direction with increased travel.2. Provides Trim.3. Realistic Control Feel by Resistance

III. RudderA. Conventional design with rudder trim.

IV. AileronsA. Differential Type

V. FlapsA. Manually controlled by a control handle attached to a

cable.B. Balanced and Spring Loaded to 0 degrees (Up).C. 0, 10, 25, 40 Degree Flap Settings.D. Can be used as step when flaps are retracted.






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FUEL SYSTEMPA-28-161 WARRIOR III

I. DescriptionA. Two 25 Gallon Fuel Tanks (24 Usable).B. Usable Fuel at Indicator Tab is 17 Gallons.C. Tank Selector: Left, Right, or OffD. Engine Driven PumpE. Auxiliary Electric Pump

1. On for Engine Start, Takeoff, Landing, Tank Switching, and Training Manuevers.

F. Electric Primer1. Momentary primer switch. 2. Activates electric fuel pump and feeds prime

lines.G. Fuel Venting

1. Accomplished through Filler Cap Vent2. Overflow drain under each wing incase of

temperature expansion.

II. Drains

A. Should be opened before flight to check for water, contaminants, and proper fuel.

B. One Drain Per Tank.C. One Drain on Fuel Strainer. Located on left side of nose

section.

III. Indications

A. Fuel Quantity and Pressure contained on common instrument face.






Date: 07/01/2012

B. Maximum Pressure:8 PSI(Red Line)

C. Minimum Pressure: .5 PSI(Red Line)

D. Green Arc: .5 PSI to 8 PSI






Date: 07/01/2012





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Original Date: 07/01/2012

PA-28-161 Fuel System

ELECTRICAL SYSTEMPA-28-161 WARRIOR III

I. Description

A. 24 Volt BatteryB. 60 Amp, 28 Volt AlternatorC. Voltage Regulator and Master Switch Relay

1. Located on the forward left side of the fuselage behind the instrument panel.

D. Ammeter1. Indicates load on alternator.

E. Circuit Breakers1. Used to protect electrical equipment from

overload or short circuit.2. If a circuit breaker pop’s in flight let it cool for two

minutes before resetting. Consider not resetting if not essential to flight.





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Circuit Breaker Panel

II. Electrical Equipment

A. Lights1. Landing, Fin/Wingtip Strobes, Recognition,

Navigation2. Panel, Avionics, Dome, Flood

B. Equipment1. Starter2. Fuel Pump3. Stall Warning Indicator4. Fuel Gauge5. Ammeter6. Annunciator Panel





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7. Flight Instruments8. Avionics

III. Emergencies

A. Refer to POH and aircraft emergency checklist.





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WARNING SYSTEMSPA-28-161 WARRIOR III

I. Annunciator Panel

A. Alternator INOPB. Oil PressureC. Vacuum INOPD. Low VoltageE. Starter EngageF. Annunciator Panel only provides a warning to the pilot

that the system is not functioning properly.

II. Stall Warning

A. Electrically PoweredB. Stall Vane on Left WingC. Horn annunciates 5-10 KIAS above stall.

PA-28-161 Annunciator Panel





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VACUUM SYSTEMPA-28-161 WARRIOR III

I. Description

A. Operates Air Driven Instruments1. Attitude Indicator2. Directional Gyro

B. Vacuum Gauge1. Maintains 4.8 to 5.2 IN Hg.2. Lower pressure than normal may indicate a dirty

filter, dirty screens, or a leak in the system.3. A zero indication indicates a sheared drive,

defective pump, or collapsed line.

Vacuum Gauge





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PITOT-STATIC SYSTEMSPA-28-161 WARRIOR III

I. Description

A. The system supplies pitot and static pressure for airspeed, altimeter, and vertical speed indications.

B. Pitot and Static Pressure picked up by Pitot Head beneath left wing.

C. Alternate Static Source1. Located beneath the left side of

instrument panel.D. Drainage

1. Via drain valves on left lower wall of cockpit.

E. Pitot Heat1. Used in case of in flight icing or heavy

rain.2. Should be “ON” in visible moisture and

low temperatures. Industry standard is within visible moisture and below 10C.





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Pitot-Static System





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ENVIRONMENTALPA-28-161 WARRIOR III

I. Description

A. Heat

1. Provided by muffler shroud.

2. Heat regulated by controls on right side of cockpit.

3. Can be used as defroster.

B. Fresh Air

1. Inlets on leading edges of wings.

2. Adjustable outlet for each seat.

3. Optional Blower Fan

A. Off, Low, Med, High





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Environmental System




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